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公开(公告)号：US11913405B2
公开(公告)日：2024-02-27
申请号：US18183232
申请日：2023-03-14
Applicant: Safran Aircraft Engines
Inventor： Fernando Gea Aguilera , Matthieu Fiack , Mathieu Simon Paul Gruber
CPC classification number: F02K1/386 , F02C7/042 , F02C7/045 , F02K1/48 , F05D2220/323 , F05D2250/183 , F05D2250/61 , F05D2260/96 , F15D1/004 , F15D1/0035
Abstract: An airflow profile structure having a leading and/or trailing edge profiled with a serrated profile having a succession of teeth and depressions. Along the leading and/or trailing edge, from a first location to a second location, the teeth of the serrated profile are individually inclined towards the second location.
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公开(公告)号：US11591913B2
公开(公告)日：2023-02-28
申请号：US15507071
申请日：2015-08-28
Applicant: Safran Aircraft Engines
Abstract: A variable-pitch bladed disc including a plurality of blades, each at a variable pitch in relation to a rotation axis of the blade and each having a root, the plurality of blades including at least one first blade and at least one second blade, a plurality of rotor connecting shafts, each having a root and a tip, each root being mounted at the tip of a corresponding rotor connecting shaft by way of a pivot so as to allow each blade to rotate about the blade rotation axis, the first blade having a first blade inclination, such that the first blade is inclined in a fixed manner with respect to the blade rotation axis of the first blade, and the second blade having a second blade inclination different from the first blade inclination.
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3.发明授权公开(公告)号：US10723434B2
公开(公告)日：2020-07-28
申请号：US15551921
申请日：2016-02-18
Applicant: SAFRAN AIRCRAFT ENGINES
Inventor： Mathieu Simon Paul Gruber , Norman Bruno Andre Jodet
Abstract: A propulsion assembly for aircraft, the assembly including a turbojet having at least one unducted propulsion propeller; and an attachment pylon for attaching the turbojet to a structural element of the aircraft, the pylon being positioned on the turbojet upstream from the propeller and having an airfoil extending transversely between a leading edge and a trailing edge, the trailing edge of the airfoil of the pylon includes a cutout extending longitudinally over a fraction of the trailing edge facing at least a portion of the propeller, the cutout being configured to increase locally the distance between the trailing edge and the propeller, the cutout presenting an outline having a curved shape presenting at least two points of inflection.
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公开(公告)号：US11772777B2
公开(公告)日：2023-10-03
申请号：US17341277
申请日：2021-06-07
Applicant: SAFRAN AIRCRAFT ENGINES
IPC: B64C11/06 , B64C11/32 , B64C11/30 , F02K3/072 , F01D1/26 , F01D7/00 , B64C11/48 , B64D27/00 , F04D29/36
CPC classification number: B64C11/30 , B64C11/06 , B64C11/32 , B64C11/48 , F01D1/26 , F01D7/00 , F02K3/072 , B64D2027/005 , F04D29/362 , F05D2220/325 , F05D2220/36 , F05D2250/314 , F05D2260/74 , F05D2260/79 , F05D2260/961 , Y02T50/60
Abstract: A variable pitch bladed disc including a plurality of blades, each being of variable pitch about a blade axis of rotation and having a root, the plurality of blades including at least one first blade and at least one second blade, a plurality of rotor connecting shafts, each shaft having a root and a tip, the root of each blade being mounted on the tip of a corresponding rotor connecting shaft via a pivot so as to allow each blade to be rotated about the blade axis of rotation, the first blade having a first rotation axis inclination such that the rotation axis thereof is inclined in a fixed manner with respect to a radial axis passing through the root of the corresponding shaft, and the second blade has a second rotation axis inclination different from the first rotation axis inclination.
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公开(公告)号：US11629664B2
公开(公告)日：2023-04-18
申请号：US16969630
申请日：2019-02-15
Applicant: Safran Aircraft Engines
Inventor： Fernando Gea Aguilera , Matthieu Fiack , Mathieu Simon Paul Gruber
Abstract: An airflow profile structure having a leading and/or trailing edge profiled with a serrated profile. The serrated profile has a succession of teeth and depressions, characterized in that, along the leading and/or trailing edge, from a first location to a second location, the teeth of the serrated profile are individually inclined towards the second location.
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Patent Agency Ranking
公开(公告)号：US20210003074A1
公开(公告)日：2021-01-07
申请号：US16969738
申请日：2019-02-15
Applicant: Safran Aircraft Engines
IPC: F02C7/045 , F02K1/38 , F15D1/00 , B64C21/10 , B64C21/02 , B64C3/14 , B64C3/16 , B64C7/02 , B64C11/18 , B64C5/00 , B64C5/06
Abstract: An airflow profiled structure having a profiled leading edge. The profiled leading edge having, along a leading edge line, a serrated profile line with a succession of teeth and depressions. The airflow profiled structure also includes a porous acoustically absorbent region located towards the bottom of the depressions.
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公开(公告)号：US11732588B2
公开(公告)日：2023-08-22
申请号：US18076976
申请日：2022-12-07
Inventor： Fernando Gea Aguilera , Raphaël Barrier , Mathieu Simon Paul Gruber , Cyril Polacsek , Hélène Dominique Jeanne Posson
Abstract: A turbomachine includes a rotor and a stator, the stator having a plurality of profiled structures, each profiled structure being elongated in a direction of elongation in which the profiled structure has a length exposed to an airflow, and having a leading edge and/or a trailing edge, at least one of which is profiled and has, in said direction of elongation, serrations defined by a succession of peaks and troughs and having a geometric pattern transformed, over at least a part of said length exposed to the airflow, by successive scaling, via multiplicative factors, in the direction of elongation and/or transverse to the direction of elongation. The geometric pattern, as defined with reference to a radial distribution of the integral scale of the turbulence, evolves in a non-periodic manner.
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公开(公告)号：US20230213000A1
公开(公告)日：2023-07-06
申请号：US18183232
申请日：2023-03-14
Applicant: Safran Aircraft Engines
Inventor： Fernando Gea Aguilera , Matthieu Fiack , Mathieu Simon Paul Gruber
IPC: F02C7/045
CPC classification number: F02C7/045 , F05D2220/323 , F05D2250/61 , F05D2260/96
Abstract: An airflow profile structure having a leading and/or trailing edge profiled with a serrated profile having a succession of teeth and depressions. Along the leading and/or trailing edge, from a first location to a second location, the teeth of the serrated profile are individually inclined towards the second location.
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公开(公告)号：US10941667B2
公开(公告)日：2021-03-09
申请号：US16174553
申请日：2018-10-30
Applicant: SAFRAN AIRCRAFT ENGINES
Inventor： Claire Marie Figeureu , Eric Pierre Georges Lemarechal , Benjamin Bulot , Mathieu Simon Paul Gruber , Raphael Barrier , Cyril Polacsek
Abstract: A stator vane including a vane root, a vane tip, a leading edge extending between the root and the tip, the leading edge having a serrated profile having a succession of teeth and of troughs each having an amplitude and a thickness, wherein a series of at least three teeth and three consecutive troughs starting from the vane root and/or from the vane tip have a growing amplitude and/or thickness.
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公开(公告)号：US11859534B2
公开(公告)日：2024-01-02
申请号：US16969738
申请日：2019-02-15
Applicant: Safran Aircraft Engines
CPC classification number: F02C7/045 , B64C3/10 , B64C11/18 , B64C21/10 , B64D33/02 , B64D33/06 , F01D9/041 , B64D2033/0206 , F05D2260/96
Abstract: An airflow profiled structure having a profiled leading edge. The profiled leading edge having, along a leading edge line, a serrated profile line with a succession of teeth and depressions. The airflow profiled structure also includes a porous acoustically absorbent region located towards the bottom of the depressions.
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